Energy efficient solid propellant attitude control system

Abstract

An energy efficient solid propellant attitude control system for use on post boost vehicles equipped with post boost control systems, post boost propulsion systems, and velocity control systems utilizes gas from a gas generator to drive a gas turbine which drives an alternator to produce electrical power. The turbine effluent gas is selectively directed to highly vectorable hinged nozzles to provide attitude control for the post boost vehicle. Power from the alternator is used to drive electromechanical actuators which orient the highly vectorable hinged nozzles. The turbine effluent gas is also selectively directed to fixed thrusters and twin axial thrust motors.

What is claimed is: 
     
       1. An energy efficient solid propellant attitude control system for a post boost space vehicle having an aft end comprising, a solid propellant gas generator for generating a flow of generated gas,   a plurality of nozzles mounted on the aft end of the post boost space vehicle for providing attitude control of the post boost space vehicle,   means directing said flow of generated gas through said nozzles to the environment to control the attitude of the post boost space vehicle, said nozzles being highly vectorable hinged nozzles having a side gas inlet through which the said flow of generated gas is admitted for flow through said nozzles to the environment,   means operative to extract surplus energy from the said flow of generated gas, before the said flow of generated gas is directed through said nozzles,   said means to extract energy from the said flow of generated gas comprising a gas turbine, a first conduit connecting said gas generator to said turbine for driving said turbine by the said flow of generated gas, said turbine having an effluent gas exit opening, and an alternator driven by the gas turbine to produce electrical power, and   means utilizing such extracted surplus energy to orient said nozzles relative to the post boost space vehicle,   wherein said means to direct said flow of generated gas through said nozzles to the environment includes a second conduit connecting the turbine gas effluent exit opening to the side gas inlet of said nozzles,   wherein said means utilizing energy that is extracted from said flow of generated gas to orient said nozzles relative to the post boost space vehicle is an electromechanical actuator that is energized by the electrical power produced by said alternator,   wherein said post boost space vehicle has a center of gravity and includes a moment arm axis associated with each of said nozzles, all of said moment arm axes passing through the center of gravity of said post boost space vehicle,   wherein each of said nozzles is vectorable substantially 90° in either direction from the associated moment arm axis of the post boost space vehicle and includes externally mounted opposed cylindrical posts rigidly formed with said nozzles with at least one of said posts being hollow and forming a side gas inlet of said nozzles, and   further including a bracket associated with each of said nozzles in which the opposed posts of the nozzle are mounted for pivotal movement, said bracket being fixedly attached to the aft end of said post boost space vehicle.   
     
     
       2. An energy efficient solid propellant attitude control system for a post boost space vehicle comprising, a solid propellant gas generator for producing a flow of generated gas, said gas generator including a casing having an exit opening for the said flow of generated gas,   a gas turbine, said turbine having an exit opening for effluent gas,   first conduit means connecting the exit opening of said gas generator casing to said gas turbine for driving said gas turbine with the said flow of generated gas, with effluent gas from said gas turbine exiting therefrom through said gas turbine exit opening,   an alternator, said alternator being connected to and driven by said turbine for producing electrical power,   a plurality of highly vectorable hinged nozzles each of which have a side gas inlet for providing attitude control for the post boost vehicle, each of said nozzles being connected to and adapted for pivotal movement relative to the post boost vehicle,   wherein each of said highly vectorable hinged nozzles is of the covergent divergent type having an inlet chamber, a throat and an expansion cone, includes externally mounted opposed cylindrical posts rigidly formed therewith with at least one of said posts being hollow and forming the side gas inlet of said nozzle, and further includes a bracket in which said opposed posts are mounted for pivotal movement, said bracket being fixedly attached to the post boost vehicle,   second conduit means connecting the said exit opening of said gas turbine to the side inlet of each of said nozzles for venting turbine effluent gas to the environment through said nozzles,   valve means connected in said second conduit means to selectively control the flow of effluent gas from said turbine through said nozzles, and   electromechanical actuator means connected to said nozzles for adjusting the orientation thereof relative to the post boost vehicle, said actuator means being connected to and driven by electrical power produced by said alternator.   
     
     
       3. An energy efficient solid propellant attitude control system for a post boost space vehicle comprising, a solid propellant gas generator for producing a flow of generated gas, said gas generator including a casing having an exit opening for the said flow of generated gas,   a gas turbine, said turbine having an exit opening for effluent gas,   first conduit means connecting the exit opening of said gas generator casing to said gas turbine for driving said gas turbine with the said flow of generated gas, with effluent gas from said gas turbine exiting therefrom through said gas turbine exit opening,   an alternator, said alternator being connected to and driven by said turbine for producing electrical power,   a plurality of highly vectorable hinged nozzles each of which have a side gas inlet for providing attitude control for the post boost vehicle, each of said nozzles being connected to and adapted for pivotal movement relative to the post boost vehicle,   second conduit means connecting the said exit opening of said gas turbine to the side inlet of each of said nozzles for venting turbine effluent gas to the environment through said nozzles,   valve means connected in said second conduit means to selectively control the flow of effluent gas from said turbine through said nozzles, and   electromechanical actuator means connected to said nozzles for adjusting the orientation thereof relative to the post boost vehicle, said actuator means being connected to and driven by electrical power produced by said alternator,   wherein said valve means includes a pivotable flapper individually associated with the side inlet of each of said nozzles with the pressure of the gas being operative to move said flapper to close said side inlet to prevent the flow of gas therethrough, and further including electromagnetic means which, when energized, is operative to move said flapper away from said side inlet to allow the flow of gas through said nozzle.